Aerospace Sciences Laboratory Tour Thomas Juliano 18 November 2009.

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Presentation transcript:

Aerospace Sciences Laboratory Tour Thomas Juliano 18 November 2009

2 Overview Aeropace Sciences Lab (ASL) houses AAE department’s aerodynamics research Please do not miss way right on approach to Runway 23 Facilities –Water tunnel –Five subsonic wind tunnels –Three supersonic wind tunnels –Hypersonic (Mach>5) wind tunnel

3 Water Tunnel 12 in. * 12 in. test section Approx 12 in./s top speed Dye injection for flow visualization Laser Doppler Velocimeter Lab class use

4 High Contraction Tunnel 18 in. diameter test section 25 m/s (56 mph) top speed Lift and drag measurement for aerodynamics lab class Drag balance for model rockets for undergrad rocketry class

5 Boeing Wind Tunnel 4 ft. * 6 ft. test section 50 m/s (112 mph) top speed 3-axis force and moment measurement Active for teaching and research projects

6 Mach 2.5 Supersonic Tunnel 2-dimensional (rectangular) nozzle with transparent side walls 2 in. * 2 in. test section 30-s run time Pressure taps, oil flow, schlieren

7 Boeing/AFOSR Mach-6 Quiet Tunnel Ludwieg Tube 6-10 s run time, about once per hour p 0 = atm, T 0 =433 K

8 Nozzle & Test Section

9 Boundary Layer Transition & Quiet Flow Boundary layer state affects surface heating, skin friction, separation, etc. Quiet flow = low ‘noise’ level = small pressure fluctuations Run start Noisy flow Intermittent noise Turbulent burst Quiet flow End of run Noise level one of several factors that contributes to boundary layer transition (geometry, Re, surface roughness, angle of attack, etc.)

10 Noise Effect on HIFiRE-5 α=0, T 0 =426 K, t=1.0 s, Smoother finish Quiet flow, M ∞ =6.0, p 0 =980 kPa, Re=10.7*10 6 /m, Noisy flow, M ∞ =5.8, p 0 =1000 kPa, Re=11.8*10 6 /m,

11 Questions

12 Mach 4 Supersonic Jet Infinite run time Approx 1 in. diameter jet Used for instrument calibration

13 Purdue Quiet-Flow Ludwieg Tube Mach 4 Testbed for BAM6QT